AFRL MicroPPT Development for Small Spacecraft Propulsion
Abstract
A class of miniaturized pulsed plasma thrusters (PPT), known as MicroPPTs, is currently in development at the Air Force Research Laboratory, Edwards Research Site, California. The MicroPPTs use a surface discharge across solid Teflon propellant to provide precise impulse bits in the 10 micro-newton-per-second range. In the near term, these thrusters can provide propulsive attitude control on 150-kg-class spacecraft using one-fifth the dry mass of conventional torque rods and reaction wheels. Eventually these thrusters are designed for primary and attitude control propulsion on future 25-kg class spacecraft. Efforts to characterize MicroPPT performance and the thruster plume are underway. To this end, a modified torsional thrust stand has been developed for the purpose of accurately measuring the low-level thrust generated by the MicroPPT. A Herriott Cell interferometer is introduced to establish the electron and neutral densities in the thruster plume. Comparison of the measured electron density with modeling predictions shows close agreement. Additionally, a Pockels cell has been developed to provide a zero-impedance MicroPPT breakdown voltage measurement, and an intensified CCD array has been used to characterize the divergence of both the thruster plume and the particulate emission. A synopsis is also presented of the status of the thruster development, including lifetime, thermal, and environmental testing.
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 2002
- Accession Number
- ADA435108
Entities
People
- Daron R. Bromaghim
- David White
- Erik L. Antonsen
- Gregory G. Spanjers
- Iain D. Boyd
- James Lake
- John H. Schilling
- Michael Keidar
- Rodney L. Burton
- Stewart Bushman
Organizations
- Air Force Research Laboratory